Assessment of go-around climb gradient for civil aircraft based on digital virtual flight
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摘要:
飞机的爬升梯度反映了其越过地面障碍达到安全高度的能力，为保障民机复飞时的飞行安全，适航条款规定复飞爬升梯度应满足一定的数值要求。根据适航条款对民机复飞程序和复飞爬升梯度的规定，提出了一种基于数字虚拟飞行的复飞爬升梯度适航符合性评估方法。基于适航条款规定和驾驶员操纵特点，建立了复飞任务的数字化模型和驾驶员操纵模型，进而以中国某型涡喷支线客机为对象建立飞行动力学模型，构成了可进行复飞爬升任务仿真的数字虚拟飞行仿真系统。通过仿真计算完成了对着陆爬升和进场爬升的爬升梯度评估，并与真实试飞结果对比，评估相对误差在10%以内，验证了本文方法的适用性和准确性。本文方法可应用于民机的概念方案设计，为保证飞机复飞爬升性能的适航符合性和最大着陆重量的确定等提供支持。
Abstract:The climb gradient of the aircraft reflects its ability of flying over the ground barrier to a safe altitude. To ensure safety of civil aircraft when going around, airworthiness regulations provide that the go-around climb gradient should meet certain numerical requirements. According to provisions of airworthiness regulations on go-around procedure and go-around climb gradient of civil aircraft, an airworthiness compliance assessment method of go-around climb gradient was proposed based on digital virtual flight. The task digitized model of go-around and pilot control model were established based on the airworthiness regulations as well as the characteristics of pilot control. Then the flight dynamics model of a certain domestic turbojet aircraft was established, which eventually constituted digital virtual flight simulation system for go-around task. The climb gradient evaluations of landing climb and approach climb were completed by flight simulation. Compared with the real flight test results, the evaluation errors are less than 10%, which verifies the applicability and accuracy of the method. This method can be applied to the design of civil aircraft, so as to provide support for determining the airworthiness compliance of go-around climb performance and the maximum landing weight of aircraft.
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图 2 基于数字虚拟飞行的适航符合性评估方法结构框图
Figure 2. Architecture of airworthiness compliance evaluation method based on digital virtual flight
图 5 复飞爬升数字虚拟飞行仿真控制结构框图
Figure 5. Control architecture of digital virtual flight simulation for go-around climb
图 7 着陆爬升过程飞行状态和控制参数时间历程曲线
Figure 7. Time history curves of flight state and control variables of landing climb
图 8 进场爬升过程飞行状态和控制参数时间历程曲线
Figure 8. Time historiy curves of flight state and control variables of approach climb
参数 取值范围 视觉反应 增益KV [1, 100] 超前时间常数TL/s [0, 1.0] 滞后时间常数TD/s [0, 1.0] 神经反应延迟τv/s [0.06, 0.20] 运动感觉反应 增益Km [1, 100] 神经反应延迟τm/s [0.06, 0.20] 肌肉作动感觉 频率ωn/(rad·s-1) 9.0 阻尼比ζ 0.7 
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表 2 着陆爬升性能试飞数据
Table 2. Flight test data of landing climb performance
参数 数值 构型参数 重量/kg 40 101.0 卡位 F4 重心 4.48%c 起落架 放下 任务参数 试验高度/m 3 000 NL/% 100 VREF/kn 130.0 NR/% 100 使用条件 静温/K 270.0 风速 0 试飞结果 爬升率/(m·s-1) 8.16 爬升梯度/% 10.4
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表 3 进场爬升性能试飞数据
Table 3. Flight test data of approach climb performance
参数 数值 构型参数 重量/kg 39 954.7 卡位 F3 重心 3.86%c 起落架 收起 任务参数 试验高度/m 3 500 NL/% 100 VREF/kn 165.2 NR 0 使用条件 静温/K 267.8 风速 0 试飞结果 爬升率/(m·s-1) 3.02 爬升梯度/% 3.08
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